AAE450 Spring 2009

Caitlyn McKay

Structures and Thermal

Locomotion Phase

1

AAE450 Spring 2009

Mass

Caitlyn McKay

Structures and Thermal

Total Mass of Rover = 29.1259 kg

Dimensions of Rover = .407 m x .497 m x .456 m2

AAE450 Spring 2009

Stress of Rover on Motor Shaft

Caitlyn McKay

Structures and Thermal

3

AAE450 Spring 2009

Stress of Rover on Shaft

Caitlyn McKay

Structures and Thermal

4

AAE450 Spring 2009

Stress of Rover on Shaft

Maximum mass for the shaft of .01 m diameter while

on the moon:

61.4 kgCaitlyn McKay

Structures and Thermal

5

AAE450 Spring 2009

Assumption: gravitational force=9.80665 m/s^2

Caitlyn McKay

Structures and Thermal

6

Diameter of Shaft Needed to Support Rover on Earth

AAE450 Spring 2009

Assumption: gravitational force = 9.80665 m/s^2

gravitational force = 7.5

Caitlyn McKay

Structures and Thermal

7

Diameter of Shaft Needed to Support Rover during

Launch

AAE450 Spring 2009

Assumption: gravitational force = 9.80665 m/s^2

gravitational force = 10

Caitlyn McKay

Structures and Thermal

8

Diameter of Shaft Needed to Support Rover during Soft

Landing

AAE450 Spring 2009

Assumption: gravitational force=9.80665/6 m/s^2

Caitlyn McKay

Structures and Thermal

9

Diameter of Shaft Needed to Support Rover on Moon

AAE450 Spring 2009

Buckling of Aluminum Body

Buckling Stress: 82,300 kg/m^2

Caitlyn McKay

Structures and Thermal

10

AAE450 Spring 2009

Energy Usage

Caitlyn McKay

Structures and Thermal

11

AAE450 Spring 2009

Operating Temperatures

Caitlyn McKay

Structures and Thermal

12

AAE450 Spring 2009

References:2008. CES EduPack2008. Citrix Client.

Purdue University, West Lafayette, IN.

Grandt, Alten F. Fundamentals of Structural

Integrity. Hoboken, NJ: John Wiley &

Sons, Inc., 2004.

Caitlyn McKay

Structures and Thermal

13